bellanca



June 30, 1931.

s. M. BELLANCA EXHAUST. MANIFOLD Originia1 Fi1ed Sept. 1 1926"ZSheets-Sheet l v gwwmm fudge e J1me 1931- ca. M. BELLANCA EXHAUS TMANIFOLD t z Filed S p 192s 2 Sheets-Sheet 2 gwuentoz fiz'weppeMafiafiel/azw Reissued June 30, 1931 I UNITED STATES PATENT GUISEPPE u.BELLA'NcA,

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OF NEW GA STLE,' DELAWARE, ASSIGNOR TO BELLANGA AIR- OF NEW CASTLE,DELAWARE, A CORPORATION OF DELAWARE EXHAUST MANIFOLD Original No.1,713,814, dated May 21,1929, Serial No. 135,710, filed September 16,1926. Application for reissue filed March 27, 1930.

This invention relates to the construction and mounting of an exhaustmanifold for aeronautical engines.

In the development of airplanes in connection with which engines of theradial and other more or less similar types are used, considerabledifficulty has been found in so mounting the exhaust manifold that itwill not present a substantial surface area to produce air resistanceand a corresponding restriction in speed of flight of the airplane.

This difliculty arises out of the necessity for mounting the exhaustmanifold outside the chamber formed by the shell of the fuselage 16 andin a disposition substantially encircling the cowl portion of thefuselage transversely to the direction of flight. The manifold by thusextending across the line of flight, presents its forward surfacethroughout its length to the resistance of the air.

A general object of the present invention is to provide an exhaustmanifold for radial aeronautical engines which will be free from theobjectionable features referred to and which will provide a minimumamount of 'air resistance.

Further objects of the invention are to minimize the eifects of thenoise produced by the discharging exhaust, to prevent overheating of themanifold, and to prevent buckling or distortion of the parts underexpansion efl'ects arising out of temperature changes.

The invention includes the mounting of the exhaust manifold in a recessor channel formed" in the surface'of the engine cowling, the manifoldbeing thereby partly or wholly protected from engagement of the rushingair therewith.

Another feature of the invention is the mounting of the manifold in aspaced apart relation to the surface of the receiving channel so thatair can flow through the space between the manifold and channel surfaceto produce a cooling effect on the manifold and prevent overheatingthereof.

Another feature of the invention is that the manifold is allowed toproject slightly outside of the surface of the cowling so as tointercept a part of the air current and direct in the use of flexibleSerial No. 439,520.

it through the space between and the channel surface.

Another feature of the invention resides in the provision of an exhaustmanifold having a formation in cross-section such as will provide aminimum air-resistanee area.

Another feature of the invention resides joints in the manifoldstructure to prevent injury to the parts by expansion and contractioneffects.

Still another feature of the invention resides in an adaptability of themanifold structure to be mounted in various positions to causethe'exhaust to be discharged at any desired point inthe length of themanifold structure. i

Other features of the invention will be hereinafter referred to.

In the drawings, in which a preferred em bodiment of the invention hasbeen selected for illustration,

Figure l is a diagrammatic view showing a portion of the forward end ofan airplane equipped with an exhaust manifold construction embodying theinvention.

Figure 2 is a sectional view on an enlarged scale taken on the line 22of Figure 1.

v Figure 3 is a detail view in perspective showlng the telescoping jointused in my improved manifold.

Figure 4 is a detail view in perspective showing the flexible joint usedin the branches of my improved manifold.

Figure 5 is a view in perspective showing the manifold structuredetached from the engine cowlingandpresenting a rearward view thereof.

Figure 6 is a sectional view. of a modification of Figure 2.

Referring to the drawings for a more .detailed description of theinvention, at 10 is shown the engine cowling portion of the fuselage ofan airplane through openings 11 in which the cylinders 12 of an engineof the radial type protrude. The forward portion of the cowling 10 isequipped with a cap member or fairing 13 designed to decrease the effectof air resistance acting on thehub portions of the propeller 14.

In order to dispose of the exhaust from the the manifold radiallydisposed cylinders 12 through a common discharge conduit an exhaustmanifold 15 is made use of which is disposed in a substantiallyencircling relation to the cowl structure 10, the location of themanifold being just to the rear. of the positions of the enginecylinders 12. Branch pipe connections 16 are provided betweenthe'exhaust discharge ports 17 of the engine cylinders 12 and themanifold 15, the manifold terminat-' ing in a discharge member 18 whichis directed rearwardly and may be extended for any desired distancealong an outer wall of the fuselage. i Y

' In order to cause the manifold'to present a minimum area of surface toprevent air resistance the manifold is mounted in a recess or groove 19formed in the outer surface of theengine cowling 10. The groove orrecess 19 extends circumferentiall around the entire surface of the cowlan this disposition of the groove provides for the mounting ofthemanifold 15 in any desired angular relation" to the cowl so as tocause the discharge member 18 to be located at the most convenientpoint. In Figure 1 of. the drawin the dischar e member '18 of' themanifo d is shown 'sposed beneath the floor wall of the fusela c, thislocation of the dischargeterminal eing useful in overcoming the effectof noises produced by the exhaust on the occupants of the compartmentsin the fuselage. 6

It will be clear that the manifold 15 may.

rotatably adjusted within the groove 19 to cause the terminaldischarging member 18 to be disposedalong either side of the fuselage orat a point to discharge above the fuselaggand the supporting win :orplane.

- thereby dissipate eat and order to revent over eating of the manifoldand t e communication of heat to the adjacent surface of the cowl 10,the manifold is so mounted as to be slightly spaced apart from theadjacent surface of the groove or recess 19as is clearly shown inFigures 1.

and 2 of the drawings. The space 20 which is thus formed provides apassageway through which air can-flow, as is indicated by v the arrowsin Fi re 2 of'the drawin to revent over eating of the ad acent parts. 11order tofacilitate the rush of airvthrough the passageway It will alsobe noted that the cross-section 20 formed between the manifold 15 andthe surface of the groove 19 the forward or leading edge 21 of themanifold is caused 'to protrude slightly be 0nd the adjacent outer su'rface of the cow 10'.to thereby function to provide a scoopin action onthe air'stream rushing rearwar. y along the surface of the cowl 10. Theair thus caught .or entrapped is diverted through the channel 20 as willbe seen and produces the cooling effect referred or formation of themanifold member 15 is a \such as to present-a degree of re- Forinstance, a nose sistance to the air. In the drawings it will be notedthat the manifold has the formation of a flattened tube with forwardlyand rearwardly extending an les and a substantially flat, outer surfacef0 lowing approximately the contour of the outer surface of. the cow]10. While this particular formation has'been found effective in practiceit will be apparent that other formations of the manifold crosssectionmay be employed with useful results.

Another feature of the invention resides in the use of flexible oryielding coupling elements in thebody structure of the manifold memberand also in the branch pipes 16 through which connections are madebetween the manifold and the engine cylinders 12. Coupling membersorjoints 22 are provided in the branch pipe connections 16 forthispurpose. These coupling members may take the form of split sleeves anexample of which sleeve being provided with a clamping boltis shown inFigure 4 of the'drawings, the- 23 and having suitable corrugations 24 toprevent slipping of the coupling member from engagement with the jointsectionsof the branch exhaust pipes 16.

In order to provide for expansion or contraction of the manifoldstructure itself under changing temperature conditions a telescopicjoint 25 is provided which permits of rela-,

tive movement of the contiguous sections of the manifold toward or fromeach other to ,7

thereby prevent distortion orother injury to the, manifold by theexpansion and contraction effects due to changes in tempera-. ture. a

In certain types of construction it is possible that the addition of theexhaust manifold of my invention may interfere with the application andremoval of the material of the cowl structure. To obviate thisdifliculty the construction indicated ilif \Figure 6 maybe used. In thisembodiment "the cowl 10 of Figures 1 and'2 may be cut into portions.portion 26 may pro,-

vided, cooperatin with a recess portion 27,

in the recess of w ich the exhaust manifold 21 may be positioned. Themanifold may 'be spaced away fromtlie member27 by a small distance asbefore to provide the passageway 20 for cooling air. This constructionpermits theready removal of the nose portion of the cowl for access tothe engine members, or of the rear portion, or of the manifold .andgrooved portion together.

As a further modification the cowl member may be separated "at twopoints as shown in Figure 6 to provide a noseporti'on 26,.a channelportion 27 and a rear portion 28.

This construction permits the removal of the.

nose portion. and the rear portion of the cowl independently of theexhaust manifold and i of the recess} portion. This modification of theconstruction provides meansv for a more in said manifold whereby toprovide for ex-.

convenient and easy structures. 4

It will-be seen that a manifold structure and a method of mounting thesame have been provided which overcomes or obviates the air resistanceeffects which are ordinarily encountered in the use of a manifoldstructure which must be disposed transversely to the line of flight ofthe airplane on which it is carried.

The language and expressions which have been employed throu hout thespecification are used as terms 0 description only and not oflimitation, and such terms are intended to include all the e uivalentsand such modifications as are possi 1e to be employed within the scopeof the invention claimed.

I claim: 1. In an exhaust manifold construction for aeronautical enginesof'the radial type,

access to the engine a cowl through which the exhaust discharging endsof the radially disposed cylinders project, said cowl being providedwith a circumscribing groove in its outer surface adjacent the enginecylinders, an exhaust manifold mounted insaid groove and adjustablecircumferentially therein, and a discharge terminal on the exhaustmanifold.

2. In an exhaust manifold construction for aeronautical engines of theradial type, a cowl through which the exhaust discharging ends of theradially disposed cylinders project, an exhaust manifold for saidcylinders mounted in circumscribing relation to the cowl, and saidmanifold being formed with flattened cross-section with its edges ar--ranged fore and aft to present a minimum degree of air resistance.

3. In an exhaust manifold construction for aeronautical engines of theradial type, a cowl through which the exhaust discharging ends of theradially disposed cylinders of the engine project, an exhaust manifoldfor said cylinders mounted in circumscribing rela tion to the cowl,branch pipe connections between the cylinders and the manifold, andflexible joint sections contained in said branch pipe connections. 4

4. In an exhaust manifold construction for aeronautical engines of theradial type, an exhaust manifold for the engine cylinders mounted in anencircling disposition with relation to the longitudinal axis of theairplane, said manifold being circumferential 1y adjustable to vary theposition of the d1scharge terminal, a yielding joint connection pansionand contraction effects, and said manifold having a flattenedcross-sectional formation designed to present a minimum of airresistance.

5. In an exhaust manifold construction for aeronautical engines of theradial type, a cowl through which the exhaust discharging ends of theradially disposed cylinders project, said cowl being provided with acircumscribing groove in its outer surface adgroove to permit a currentof air to pass therethrough, a flexible joint in said manifold, branchpipe connectionsbetweeii said cylinders and said manifold, and flexiblejoint sections in said branch connections.

6. In an exhaust manifold construction for aeronautical engines, a cowlfor the engine provided with a circumferential groove in its outersurface, an exhaust manifold mounted in and extending along said groove,said manifold having its underside formed in complement to the formationof the surface of the groove but spaced therefrom, the outer surface ofthe manifold being substantially flat and conforming approximately tothe formation of the cowl ward edge of the manifold protruding slightlybeyond the contour of the cowl surface whereby to deflect air throughthe space between the manifold and the surface of the groove.

7 In an exhaust manifold construction for aeronautical engines of theradial type, a cowl through which the exhaust discharging ends of theradially disposed cylinders project, said cowl being provided with acircumscribing groove in its outer surface adjacent the enginecylinders, said cowl comprising separable portions, whereby a partthereof may be removed independently of said exhaustmembers, an exhaustmanifold mounted in said groove, said manifold being circumferentiallyadjustable in said groove and spaced from the walls of the groove topermit a current of air to pass therethrough, a flexible joint in saidmanifold, branch pipe connections between said cylinders and saidmanifold, and flexible joint sections in said branch connections. i

8. In anexhaust manifold construction for aeronautical engines of theradial type, a cowl through which the exhaust discharge end of theradially disposed cylinders project,

an exhaust manifold for said cylinders mounted in circumscribingrelation to the cowl, said manifold being flattened in' cross sectionwith its longer dimension extending fore and aft and substantially flushwith the cowling.

9. In an airplane, cowl for covering the forward portion of theairplane, said cowl surface, and the forthe airplane, said cowl beingprovided with a circumferential groove in its outer surface, and anexhaust manifold nested within said groove and being :so formed that itsouter surface forms substan- I a tially a continuation of the outersurface of -thecwl.

11. In an airplane, a cowl for covering the forward portion of theairplane, said cowl being provided with a circumferential groove n inits outer surface, and an exhaust manifold nested within said groove andbeing so formed that its outer surface forms substantially acontinuation of the outer surface of Y the cowl and its leading edgeprojects slightly 1 outside the surface of the cowl.

12. A circular exhaust manifold for radial and similar engines, saidmanifoldha'ving a flattened cross section, the shortest dimension of itscross section being radial, adapted to 2.0 fit in a cowling groove withthe'outer surface substantially flush with the surface thereof. 13. Anexhaust manifold having the outer surface thereof substantially flushwith, and forming a substantial continuation of an airplane cowling, themanifold being positioned with re t to the cowling to direct air overthe enti e surface of the manifold.

' 14. In an airplane, a cowl covering the forward portion thereof, saidcowl being provided with a circumferential depression in its outersurface, and an exhaust manifold nested within said depression and beingso formed that its outer surface forms substantially a continuation ofthe outer surface of 86' the cowl. a 15. An exhaust manifold having theouter I I surface thereof flattened and substantially fiush with andforming a substantial continuation of an airplane cowling, the manifold40 having a single exhaust outlet, and being so positioned with respectto the cowling as to allow for the direction of a current of air oversubstantially the entire surface thereof. 16: A circular exhaustmanifold for radial '45 and similar engines, said manifold having a.flattened'cross section, the shortest dimension of its cross sectionbeing radial, one face being-adapted to fit in a depression in an air-'plane cowling, and the other face adapted to be substantially flushwith, and forming a continuation of the cowling surface.

In" testimony whereof I afiix my si ature. GUISEPPE M. BELLA CA.

